Ice detection system and method

ABSTRACT

An ice detection system, in particular a method, apparatus and controller for detecting icing conditions and the presence of ice formed on a structure. Also, a method, apparatus and controller to detect the prevailing environmental conditions to determine whether or not ice may form on a structure. Two heaters of an ice protection system (experiencing substantially the same environmental conditions) are driven to different temperatures (the first greater than or equal to 0° C., and the second less than 0° C.). A difference in the powers required to drive the two heaters indicates the prevailing environmental conditions. In another embodiment, a heater of an ice protection system is driven and the rate of change of surface temperature is measured over several periods. A substantial deviation from a rate of change of surface temperature, which indicates the presence of ice on the surface of the structure, is detected.

This is a divisional of application Ser. No. 12/879,179, filed Sep. 10,2010, the disclosure of which is incorporated by reference in itsentirely herein.

FIELD OF THE INVENTION

The present invention relates to an ice detection system, in particularto a system for detecting icing conditions and a system for detectingthe presence of ice formed on a structure, and the methods for doing thesame.

BACKGROUND OF THE INVENTION

Devices for detecting the presence of ice on structures, for exampleaircraft structures, are known. Example devices include those thatdetect ice formation using optical means (i.e. detecting a change inopacity or refractive index around a sensor). Others include those thatmonitor changes in a resonant frequency of a structure (i.e. theaccumulation of ice on a structure alters its resonant frequency).

We have appreciated the disadvantages of known devices for detecting thepresence of ice, and the need for an improved device.

SUMMARY OF THE INVENTION

The present invention provides a method of detecting an icing conditionin which ice may form on a structure, the method comprising: supplying afirst heater with a first power, the first heater being in thermalcontact with a first region of a structure, and the first power beingsufficient to heat the first region of the structure to a firsttemperature; supplying a second heater with a second power, the secondheater being in thermal contact with a second region of a structure, andthe second power being sufficient to heat the second region of thestructure to a second temperature; and comparing the first and secondpowers to detect a difference between the first and second powers, thedifference indicating an icing condition, wherein the first and secondregions are subjected to substantially the same environmentalconditions, and wherein the first temperature is higher than the secondtemperature.

By using this method, the prevailing conditions may be detected using anice protection system already installed in the structure.

Preferably, the first temperature is greater than or equal to 0° C., andthe second temperature is less than 0° C. More preferably, the firsttemperature is between 3° C. to 5° C., and the second temperature isbetween minus 3° C. to minus 5° C.

In embodiments, the difference between the first and second powersindicative of an icing condition is two or more times greater than thesecond power.

In some embodiments, the method is repeated periodically. Preferably,when repeated, the first heater is supplied with the second power toheat the first region to the second temperature, and the second heateris supplied with the first power to heat the second region to the firsttemperature. Preferably, the repeating interval is substantially 30seconds.

The present invention also provides apparatus for detecting an icingcondition in which ice may form on a structure, the apparatuscomprising: a first and second heater mat thermally coupleable to astructure for heating a respective first and second region of astructure adjacent to the respective first and second heater mats; afirst and second temperature sensor for outputting respective first andsecond temperature sensor signals indicative of a respective first andsecond temperatures of the respective first and second regions; acontroller for controllably applying power to the first and secondheater mats, the controller being adapted to: supply a first and secondpower to the respective first and second heater mats, the first powerbeing sufficient to heat the first region of a structure to a firsttemperature and the second power being sufficient to heat the secondregion of a structure to a second temperature; receive first and secondtemperature sensor signals from the respective first and secondtemperature sensors; and compare the first and second powers to detect adifference between the first and second powers indicative of an icingcondition, wherein the first and second regions are located so as toexperience substantially the same environmental conditions, and whereinthe first temperature is higher than the second temperature.

Using this apparatus allows a user to detect whether the prevailingenvironmental conditions are conducive to icing on a structure.

Preferably, the first temperature is greater than or equal to 0° C., andthe second temperature is less than 0° C. More preferably, the firsttemperature is between 3° C. to 5° C., and the second temperature isbetween minus 3° C. to minus 5° C.

In embodiments of the apparatus, the difference between the first andsecond powers indicative of an icing condition is two or more timesgreater than the second power.

The present invention also provides a controller for detecting an icingcondition in which ice may form on a structure, the controller forcontrolling an ice protection system, the controller comprising: anoutput adapted to supply a first and second power to a respective firstand second heater mat of an ice protection system, the first and secondheater mat being thermally coupleable to a structure for heating arespective first and second regions of a structure adjacent to arespective first and second heater mat; and an input adapted to receivea first and second temperature sensor signal from a respective first andsecond temperature sensor, the first and second temperature sensorsignals indicating a temperature at a first and second region of asurface adjacent to a respective first and second heater mat, thecontroller being adapted to: supply the first and second power to arespective first and second heater mats, the first power beingsufficient to heat the first region of a structure to a firsttemperature and the second power being sufficient to heat the secondregion of a structure to a second temperature; receive first and secondtemperature sensor signals from a respective first and secondtemperature sensor; and compare the first and second powers to detect adifference between the first and second powers indicative of an icingcondition, wherein the first and second regions are located so as toexperience substantially the same environmental conditions, and whereinthe first temperature is higher than the second temperature.

By using such a controller, an ice protection system installed in astructure may be adapted to detect icing conditions.

Preferably, the first temperature is greater than or equal to 0° C., andthe second temperature is less than 0° C. Preferably, the firsttemperature is between 3° C. to 5° C., and the second temperature isbetween minus 3° C. to minus 5° C.

In embodiments of the controller, the difference between the first andsecond powers indicative of an icing condition is two or more timesgreater than the second power.

The present invention also provides a method of detecting ice formed ona structure, the method comprising: supplying power to a heater mat, theheater mat being in thermal contact with a structure on which ice is tobe detected, and the power being sufficient to heat a surface of astructure adjacent the heater mat to greater than 0° C.; measuring asurface temperature of the structure adjacent the heater mat over afirst and second period; determining a first and second rate of changeof surface temperature over the respective first and second periods;comparing the determined first and second rate of change of surfacetemperature to determine a difference between the first and second rateof change of surface temperature; and detecting ice formed on astructure based on a difference between the first and second rate ofchange of surface temperature being greater than a threshold value.

By using such a method, the formation of ice on a structure may bedetected by using an ice protection systems already installed in thestructure.

In embodiments of this method, the threshold value is determined from amodel of the rate of change of surface temperature for the structurehaving no ice on the surface.

In embodiments, measuring the surface temperature of the structurecomprises determining the surface temperature from a sensor mountedadjacent to, and in thermal contact with, the heater mat.

In some embodiments, determining a difference between the first andsecond rate of change of surface temperature comprises determining themagnitude of the difference between the first and second rate of change.

The present invention also provides a method of detecting ice formed ona structure, the method comprising: supplying power to a heater mat, theheater mat being in thermal contact with a structure on which ice is tobe detected, and the power being sufficient to heat a surface of astructure adjacent the heater mat to greater than 0° C.; measuring asurface temperature of the structure adjacent the heater mat over afirst period; comparing the measured surface temperature over the firstperiod with a model defining surface temperature characteristics of thestructure and heater mat; and detecting ice formed on a structure basedon a difference between the measured surface temperature and the model.

The present invention also provides apparatus for detecting ice formedon a structure, the apparatus comprising: a heater mat thermallycoupleable to a structure for heating a first region of a structureadjacent to the heater mat; a temperature sensor for outputting atemperature sensor signal indicative of a temperature of the firstregion; a controller for controllably applying power to heater mat, thecontroller being adapted to: supply a first power to the heater mat, thefirst power being sufficient to heat the first region of a structure togreater than 0° C.; receive a temperature sensor signal indicative of atemperature of the first region; determine a first and second rate ofchange of surface temperature over a respective first and second period;compare the determined first and second rate of change of surfacetemperature to determine a difference between the first and second rateof change of surface temperature; and detect ice formed on a structurebased on a difference between the first and second rate of change ofsurface temperature being greater than a threshold value.

By using this apparatus, ice may be detected on the surface of astructure.

In embodiments of this apparatus, the threshold value is determined froma model of the rate of change of surface temperature for the structurehaving no ice on the surface.

In embodiments, the temperature sensor is mounted adjacent to, and inthermal contact with, the heater mat.

In embodiments, the controller is adapted to determine the magnitude ofthe difference between the first and second rate of change.

The present invention also provides a controller for detecting iceformed on a structure, the controller for controlling an ice protectionsystem, the controller comprising: an output adapted to supply a firstpower to a heater mat of an ice protection system, the heater mat beingthermally coupleable to a structure for heating a first region of astructure adjacent to the heater mat; and an input adapted to receive atemperature sensor signal from a temperature sensor, the temperaturesensor signal indicating a temperature at a first region of a surfaceadjacent to a heater mat, the controller being adapted to: supply afirst power to the heater mat, the first power being sufficient to heatthe first region of a structure to greater than 0° C.; receive atemperature sensor signal indicative of a temperature of the firstregion; determine a first and second rate of change of surfacetemperature over a respective first and second period; compare thedetermined first and second rate of change of surface temperature todetermine a difference between the first and second rate of change ofsurface temperature; and detect ice formed on a structure based on adifference between the first and second rate of change of surfacetemperature being greater than a threshold value.

By using such a controller, an ice protection system already present ina structure may be driven to detect whether or not ice has formed on thestructure.

In embodiments, the threshold value is determined from a model of therate of change of surface temperature for the structure having no ice onthe surface.

In some embodiments, the controller is adapted to determine themagnitude of the difference between the first and second rate of change.

The present invention also provides an aircraft comprising the apparatusas described above, wherein the heater mats are thermally coupled to theaircraft structure.

The present invention also provides an aircraft comprising: a de-icingsystem comprising one or more heater mats thermally coupled to astructure of the aircraft; and a controller as described above.

Although each aspect and various features of the present invention havebeen defined hereinabove independently, it will be appreciated that,where appropriate, each aspect can be used in any combination with anyother aspect(s) or features of the invention. In particular, featuresdisclosed in relation to apparatus aspects may be provided inappropriate form in relation to method aspects, and vice versa.

BRIEF DESCRIPTION OF THE DRAWINGS

Embodiments of the present invention will now be described withreference to the accompanying drawings, in which:

FIG. 1 is an illustration of the placement of heater mats and heaterzones of an ice protection system of an aircraft;

FIG. 2 is a schematic showing the placement of heater elements within aheater zone;

FIG. 3 is a cross-section of the structure of an aircraft wing section;

FIG. 4 shows a graph of the rise in temperature over time as a heatermat of a de-icing system is supplied with power;

FIG. 5 is an illustration of thermal resistances and thermalcapacitances of the wing section of FIG. 3;

FIG. 6 is a graph illustrating the variation of temperature overdistance within the wing section of FIG. 3;

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

In brief, the present invention utilises an ice protection systemalready installed in a structure (for example an aircraft structure) todetect the presence of ice formed on the surface of the structure. Thepresent invention may also be used to detect the presence of ice in theprevailing environmental conditions surrounding the structure, whichindicates to a user that ice may be likely to form on the structure. Thepresent invention may also be used to give an indication of theconcentration of ice in the surrounding environment, or formed on thestructure.

Ice protection systems protect against the build-up of ice onstructures. One common application of ice protection systems is onaircraft. During flight, the surfaces of an aircraft can be exposed towater at low temperatures and, if no preventative action is taken, icecan quickly form on the wings, on control surfaces, and on other partsof the aircraft in such a way as to alter the aerodynamic performance ofthe aircraft (for example by altering the airflow around the aircraftand by adding additional weight to it) with potentially catastrophicconsequences. Example ice protection systems are discussed in thefollowing patents and applications in the name of Ultra ElectronicsLimited (the content of which are hereby incorporated in their entiretyby reference): U.S. Pat. No. 7,580,777, WO2008/145985, US20090149997,US20090230239 and U.S. Ser. No. 12/666,776.

Electrothermal ice protection systems comprise a number of heaterdevices (such as heater mats), which can be used as anti-icing zones inwhich a sufficient temperature is maintained at the surface of the wingin order to prevent the formation of ice on and behind the protectedzone. These heater devices can also be used as de-icing zones to shedice that has been allowed to accrete on the protected region. Thede-icing mats are cyclically energised in order to melt the interfacebetween the wing and the accreted ice, causing the ice to be shed.

In such an ice protection system it is important to avoid overheating ofthe heater devices (heating mats) in order to avoid a failure either ofthe devices or in the structure to which the devices are attached. Manymodern aircraft (and other structures) use composite materials, whichcan suffer damage (delamination of the material, for example) at arelatively low temperature. Temperature ‘overshoot’ of the heaterdevices must therefore be controlled whilst maintaining rapid heating ofthe protected surface(s).

Aircraft are normally subject to a range of different icing conditionsduring flight, such as different air temperatures, air velocities,relative humidity, and so on, which can depend for example on thelocation, altitude, orientation, air speed or pitch of the aircraft, theprevailing meteorological conditions, and so on. Different icingconditions can determine not only the temperatures and velocities (andso on) at which ice will form on different parts of the aircraftstructure, but also the heat loss from the aircraft structure.

FIG. 1 is an illustration of a portion of an aircraft, showing theplacement of heater mats and heater zones of an ice protection system ofan aircraft. The aircraft 100 includes a fuselage portion 102 and a wingportion 104. On the leading edge 106 of the wing 104 are provided aplurality of heating mats 108, 110, 112 and others (not shown).

Each heater mat is divided into a number of heater zones. The number andsize of the heater zones are chosen to suit a particular safety model,for example such that up to two heater zones can fail without causing ahazardous or catastrophic failure of the aircraft. In one aircraftdesign, safety requirements require each heater mat 110 to be dividedinto six separate heater zones 114, 116, 118, 120, 122, 124.

FIG. 2 shows the structure of a heater zone. The heater zone 200comprises an upper de-icing element 202, a central anti-icing element204, and a lower de-icing element 206. The elements take the form ofresistance heater material arranged in a serpentine configuration andembedded within the heater mat. The elements are provided with contacts208 to allow power to be applied to the element.

In accordance with known de-icing techniques, the de-icing system, in ade-icing mode, maintains the anti-icing element 204 at a temperaturesufficient to prevent ice forming above the element, and intermittentlycycles power to the de-icing elements 202, 206 to shed any ice formedabove them by run-back water from the anti-icing zone, for example.

FIG. 3 is a cross-section 300 of the structure of an aircraft wingsection. The figure shows the leading edge 302 of the wing incross-section and an approximation of the airflow 304 over the wingwhilst in flight. The wing includes an erosion shield 306, typically astiff, erosion-resistant aluminium shield, a dielectric (insulator) 308,a heater mat 310, another dielectric 312, and a temperature probe 314.The layers 306, 308, 310, 312 are much thinner than as shown, forming athin sandwich at the edge of the wing section.

The main wing section 302 is formed from any appropriate material, suchas composite materials that comprise a plurality of layers of stiffmaterial bound together with glue.

Composite materials have a good ratio of strength to weight, but aresusceptible to failure by delamination (when the glue melts) at arelatively low temperature. Therefore care needs to be taken to avoid‘overshoot’ (overheating) of the heater mat.

It will be appreciated that a similar arrangement may be provided onother exposed parts of the aircraft structure (such as on propellerleading edges or on engine inlets, for example). It will also beappreciated that the temperature sensor 314 may be located between theheater mat 310 and the erosion shield 306.

Detecting Icing Conditions

In a first aspect of the invention, a controller (not shown in anyfigures) controls the ice protection system in an Icing ConditionsDetection (ICD) mode. In this mode, the ice protection system is drivento detect ice in the prevailing environmental conditions in which thestructure is placed.

In the ICD mode, first and second heater mats 306 are supplied withrespective first and second powers. First and second heater mats arechosen such that they experience substantially the same environmentalconditions as each other. For example, each of the first and secondheater mats may be on the leading edge of the same wing of an aircraft.Alternatively, the first and second heater mats may be on leading edgesof different wings. So long as the heater mats experience the sameenvironmental conditions, any combination of heater mats may be chosen.

The first heater mat is driven to achieve a first surface temperature ata first region of the structure adjacent the first heater mat. Likewise,the second heater mat is driven to achieve a second surface temperatureat a second region of the structure adjacent the second heater mat.

The first surface temperature is greater than the second surfacetemperature. Preferably, the first surface temperature is greater thanor equal to 0° C., and the second surface temperature is less than 0° C.In practice, the desired first surface temperature is between 3 to 5°C., and the second desired surface temperature is −3° C. to −5° C.

The controller controls the heater mats to achieve the desired surfacetemperatures according to the preferred methods discussed in thebefore-mentioned patents and applications in the name of UltraElectronics Limited. As well as monitoring the surface temperature, thecontroller monitors the power delivered to the first and second heatermats.

In the situation where the prevailing environmental conditions are notconducive to ice formation (i.e. temperature is too high, liquid watercontent is too low etc), the first and second powers will besubstantially similar.

However, in the situation where the prevailing environmental conditionsare conducive to icing, then there will be a difference in the powerlevels supplied to the first and second mats. Surprisingly, it has beenfound that the power required to drive the first heater mat (i.e. toachieve a surface temperature greater than or equal to 0° C.) will begreater than the power supplied to the second heater mat (i.e. toachieve a surface temperature less than 0° C.). In some conditions, thedifference was found to be in the order of two or more times greater.

The substantial difference in power requirement is as a result of thefirst heater mat having to overcome an energy deficit caused by theabsorption of heat by water or ice particles in the environmentsurrounding the structure as they impinge on the surface of thestructure.

The controller is adapted to detect this difference in power and alert auser to the fact that the structure is in an environment where ice mayform due to the prevailing conditions. The user may then choose toactivate the ice protection system manually to ensure that ice does notform on the structure.

Alternatively, the controller may automatically activate the iceprotection system in order to prevent ice forming on the surface of thestructure in response to the detection of prevailing environmentalconditions that are conducive to ice forming on a structure.

Furthermore, it is has been found that the system may determine ameasure of the concentration of the water or ice particles in theprevailing environment. If the performance of the structure comprisingthe heater mats is know for dry or non-ice conditions, then anydifference of the power drawn to achieve the desired surfacetemperatures in a different environment enables the system to determinea concentration of the water or ice particles in the prevailingenvironment. It has been found that the difference in power required toachieve the desired temperatures in a non-dry condition is proportionalto the concentration of water or ice particles in the environment.

The performance of the structure in a dry, or non-ice condition may beknow for example by generating a model of the power consumed by the matsin achieving the desired first and/or second temperatures in dry ornon-ice conditions.

Detecting Ice Formed on a Structure

In a related aspect, the controller controls the ice protection systemin an Ice Detection (ID) mode. In this mode, the ice protection systemis driven to detect ice that has already formed on the structure.

In brief, a heater mat is supplied with power, and the surfacetemperature is monitored over time by the controller, which looks forchanges in the rate of change of temperature over time.

FIG. 4 shows a graph of the rise in temperature over time as the heatermat is supplied with power.

Line 402 shows the rise in temperature over time as the heater mat issupplied with power when there is no ice present on the structure. Line404 shows the rise in temperature over time as the heater mat issupplied with power when there is ice present on the structure. As canbe seen, line 404 comprises portion 404 a where the rate of change oftemperature over time decreases (shown here as a flat portion). The rateof change of temperature than begins to rise again (portion 404 b) untila desired temperature is reached (or, in a fixed power system, where thetemperature for that power is reached).

In practice, the variation in the rate of change of temperature overtime occurs around approximately 0° C., as the ice on the structureabsorbs heat (and therefore energy), melts and transitions from a solidto a liquid. Once melted, the rate of change of temperature increases asthe surface temperature is able to rise.

As such, it is possible to detect the presence of ice on a structure bymonitoring the rate of change of temperature over time and detecting anysudden variations in that rate of change and comparing that change inthe rate of change to a threshold value. Ice can be detected from eitheror both the sudden decrease (404 a) and the sudden increase (404 b).Since one transition (404 a) will have a negative change in the rate ofchange, and the other (404 b) a positive change in the rate of change, amagnitude can be determined from the negative and/or positive rates ofchange, and compared to the threshold value.

This method may be performed by the controller.

Alternatively a pattern matching method may be used, where thetemperature rise over time (for a given power) for the structure withoutice on the surface is known (for example by storing in a model), and thecontroller compares the shape of the measured curve to that stored inthe model. Any variations from the known model may indicate the presenceof ice on the surface of the structure.

As discussed above, a concentration of the ice formed on the structuremay be determined by the system. As with the above embodiments, thepower used to achieve a desired temperature on the structure is comparedto the power used to achieve the same temperature when in a non-ice ordry condition (for example from a model). A difference in the requiredand known powers enables a concentration of ice formed on the structureto be determined, since the difference is proportional to theconcentration of ice.

Once the controller detects the presence of ice on the surface of thestructure, it may produce a warning for a user to initiate a de-icingmode of the de-icing system.

Alternatively, the controller may automatically initiate a de-icing modeof the de-icing system.

In the above embodiments, it is desirable for the controller to operatebased on temperature signals indicative of the surface temperature ofthe structure. As would be appreciated by the skilled reader, it is notalways possible for the sensor to be placed directly on the surface(whether internal or external) of the structure (for example an aircraftwing). The temperature sensor 314 is often placed away from the surfaceof the structure (with the heater mat in between the sensor and theexternal surface of the structure). As such, it can be difficult todetermine a measurement of the external surface temperature, from whichthe controller may control the various modes.

One such solution to this problem is discussed in Ultra ElectronicsLimited's earlier application.

FIG. 5 is an illustration of thermal resistances and thermalcapacitances of the wing section of FIG. 3.

The thermal resistances (degree of thermal insulation) and thermalcapacitances (heat capacity) are illustrated using electricalequivalents, with heat flow corresponding to electrical current andtemperatures corresponding to voltages. In this representation, the heatgenerated by the heater mat is represented by a current sourceQ_(HEAT INPUT) and the temperature sensor 314 of FIG. 3 is representedas a voltage measurement. Each of the layers has an associated thermalcapacity (which may be negligible) and the thermal resistance of eachlayer is also shown. The heat loss at the breeze surface (the interfacewith the air impinging on the wing), Q_(HEAT LOSS (BREEZE)), and theheat loss into the interior of the wing, Q_(HEAT LOSS (INTERIOR)), arealso indicated (as currents flowing out of the thermal circuit). Theheat loss Q_(HEAT LOSS (INTERIOR)) into the interior of the structure isconsiderably less than the heat loss Q_(HEAT LOSS (BREEZE)) through theerosion shield (by design).

The thermal properties of the wing section during normal ice protectionconditions (during flight) will now be described in more detail.

FIG. 6 is a graph illustrating the variation of temperature overdistance within the wing section of FIG. 3. The temperature 502 isplotted from the left hand side 504, where large amounts of heat flowthrough the erosion shield, to the right hand side 506, where heat isslowly lost into the wing structure. The gradient of the curve 502 isequivalent to the thermal gradient (although not drawn to scale).

The heater Temperature T_(HEATER), the temperature sensor temperatureT_(SENSOR) and the erosion shield temperature T_(ES) are indicated onthe temperature curve 502. The temperature sensor temperature T_(SENSOR)is approximately equal to the heater mat Temperature T_(HEATER) becauseof the shallow thermal gradient flowing into the structure 506. Theerosion shield temperature T_(ES) is quite different, however, becauseof the steep temperature gradient flowing out of the wing 504. Inaccordance with the electrical analogy in FIG. 4, the temperature T issubstitutable for a voltage, and a corresponding current can be derivedfrom the gradient of the curve 502.

As such, the temperature of the surface can be determined from the knownproperties of the component parts of the surface, the known amount ofpower supplied to the heater mat, and from a measurement of thetemperature sensor adjacent the heater mat.

Although the present invention has been described hereinabove withreference to specific embodiments, the present invention is not limitedto the specific embodiments and modifications will be apparent to askilled person in the art which lie within the scope of the presentinvention. Any of the embodiments described hereinabove can be used inany combination.

Although embodiments of the present invention have been described withreference to an aircraft structure, the present invention is applicableto any engineering structure, including static structures such asbridges and oil rigs, or wind turbines. In such static structures a modeof operation comprises a mode of use e.g. loading on a bridge ordrilling operations performed on an oil rig. Furthermore, aspects of theembodiments described can be implemented either in software or hardware.

What is claimed is:
 1. A method of detecting an icing condition in whichice may form on a structure, the method comprising: supplying a firstheater with a first power, the first heater being in thermal contactwith a first region of a structure, and the first power being sufficientto heat the first region of the structure to a first temperature;supplying a second heater with a second power, the second heater beingin thermal contact with a second region of the structure, and the secondpower being sufficient to heat the second region of the structure to asecond temperature; and comparing the first and second powers toidentify a difference between the first and second powers; and detectingan icing condition when the difference between the first and secondpowers is substantial, wherein the first and second regions aresubjected to substantially the same environmental conditions, andwherein the first temperature is higher than the second temperature. 2.A method according to claim 1, wherein the difference between the firstand second powers indicative of an icing condition is two or more timesgreater than the second power.
 3. A method according to claim 1, furthercomprising determining a concentration of water or ice particles in theenvironmental conditions, the determining comprising: comparing thefirst or second powers with a model defining first and second powerssufficient to drive the respective first or second heater mats such thatthe first or second regions are heated to the respective first andsecond temperatures when the first and second regions are in a non-icingcondition; and determining a concentration of water or ice particles inthe environmental conditions based on a difference in the compared firstor second powers and the first or second powers defined in the model. 4.A method according to claim 1, wherein the first temperature is greaterthan or equal to 0° C., and the second temperature is less than 0° C. 5.A method according to claim 4, wherein the first temperature is between3° C. to 5° C., and the second temperature is between minus 3° C. tominus 5° C.
 6. A method according to claim 1, wherein the method isrepeated periodically.
 7. A method according to claim 6, wherein, whenrepeated, the first heater is supplied with the second power to heat thefirst region to the second temperature, and the second heater issupplied with the first power to heat the second region to the firsttemperature.
 8. A method according to claim 6, wherein the repeatinginterval is substantially 30 seconds.
 9. A method of detecting iceformed on a structure, the method comprising: supplying power to aheater mat, the heater mat being in thermal contact with a structure onwhich ice is to be detected, and the power being sufficient to heat asurface of a structure adjacent the heater mat to greater than 0° C.;measuring a surface temperature of the structure adjacent the heater matover a first and second period; determining a first and second rate ofchange of the surface temperature over the respective first and secondperiods; comparing the determined first and second rate of change of thesurface temperature to determine a difference between the first andsecond rate of change of the surface temperature; and detecting iceformed on the structure based on a difference between the first andsecond rate of change of the surface temperature being greater than athreshold value.
 10. A method according to claim 9, wherein thethreshold value is determined from a model of a rate of change of thesurface temperature for the structure having no ice on the surface. 11.A method according to claim 9, wherein measuring the surface temperatureof the structure comprises determining the surface temperature from asensor mounted adjacent to, and in thermal contact with, the heater mat.12. A method according to claim 9, wherein determining a differencebetween the first and second rate of change of the surface temperaturecomprises determining the magnitude of the difference between the firstand second rate of change.
 13. A method according to claim 9, furthercomprising determining a concentration of ice formed on the structure,the determining comprising: comparing the power supplied to the heatermat with a model defining powers sufficient to drive the heater mat suchthat the surface of a structure adjacent the heater mat to greater than0° C. when a structure is in a non-icing condition; and determining aconcentration of ice formed on the structure based on a difference inthe compared power and the power defined in the model.
 14. A method ofdetecting ice formed on a structure, the method comprising: supplyingpower to a heater mat, the heater mat being in thermal contact with astructure on which ice is to be detected, and the power being sufficientto heat a surface of a structure adjacent the heater mat to greater than0° C.; measuring a surface temperature of the structure adjacent theheater mat over a first period; comparing the measured surfacetemperature over the first period with a model defining surfacetemperature characteristics of the structure and heater mat; anddetecting ice formed on the structure based on a difference between themeasured surface temperature and the model.
 15. A method according toclaim 14, wherein the model defining surface temperature characteristicsof the structure and heater mat comprises data defining a temperaturecharacteristic for a power supplied to the heater mat when the structurehas no ice on the surface or when the structure is in a non-icingcondition.
 16. A method according to claim 14, comprising determining aconcentration of ice formed on the structure by: comparing the powersupplied to the heater mat with a model defining powers sufficient todrive the heater mat such that the surface of the structure adjacent theheater mat to greater than 0° C. when a structure is in a non-icingcondition; and determining a concentration of ice formed on thestructure based on a difference in the compared power and the powerdefined in the model.
 17. An apparatus for detecting ice formed on astructure, the apparatus comprising: a heater mat thermally coupleableto a structure for heating a first region of a structure adjacent to theheater mat; a temperature sensor for outputting a temperature sensorsignal indicative of a temperature of the first region; a controller forcontrollably applying power to the heater mat, the controller beingadapted to: supply a first power to the heater mat, the first powerbeing sufficient to heat the first region of a structure to greater than0° C.; receive a temperature sensor signal indicative of a temperatureof the first region; determine a first and second rate of change of thesurface temperature over a respective first and second period; comparethe determined first and second rate of change of the surfacetemperature to determine a difference between the first and second rateof change of the surface temperature; and detect ice formed on thestructure based on a difference between the first and second rate ofchange of the surface temperature being greater than a threshold value.18. An apparatus according to claim 17, wherein the threshold value isdetermined from a model of the rate of change of the surface temperaturefor the structure having no ice on the surface.
 19. An apparatusaccording to claim 17, wherein the temperature sensor is mountedadjacent to, and in thermal contact with, the heater mat.
 20. Anapparatus according to claim 17, wherein the controller is adapted todetermine the magnitude of the difference between the first and secondrate of change.
 21. An apparatus according to claim 17, wherein thecontroller is adapted to determine a concentration of ice formed on thestructure by: comparing the power supplied to the heater mat with amodel defining powers sufficient to drive the heater mat such that thesurface of the structure adjacent the heater mat to greater than 0° C.when the structure is in a non-icing condition; and determining aconcentration of ice formed on the structure based on a difference inthe compared power and the power defined in the model.
 22. An aircraftcomprising the apparatus according to claim 17, wherein the heater matsare thermally coupled to the aircraft structure.
 23. A controller fordetecting ice formed on a structure, the controller for controlling anice protection system, the controller comprising: an output adapted tosupply a first power to a heater mat of an ice protection system, theheater mat being thermally coupleable to a structure for heating a firstregion of a structure adjacent to the heater mat; and an input adaptedto receive a temperature sensor signal from a temperature sensor, thetemperature sensor signal indicating a temperature at a first region ofa surface adjacent to a heater mat, the controller being adapted to:supply a first power to the heater mat, the first power being sufficientto heat the first region of the structure to greater than 0° C.; receivea temperature sensor signal indicative of a temperature of the firstregion; determine a first and second rate of change of the surfacetemperature over a respective first and second period; compare thedetermined first and second rate of change of the surface temperature todetermine a difference between the first and second rate of change ofthe surface temperature; and detect ice formed on the structure based ona difference between the first and second rate of change of the surfacetemperature being greater than a threshold value.
 24. A controlleraccording to claim 23, wherein the threshold value is determined from amodel of the rate of change of the surface temperature for the structurehaving no ice on the surface.
 25. A controller according to claim 23,wherein the controller is adapted to determine the magnitude of thedifference between the first and second rate of change.
 26. A controlleraccording to claim 23, wherein the controller is adapted to determine aconcentration of ice formed on the structure by: comparing the powersupplied to the heater mat with a model defining powers sufficient todrive the heater mat such that the surface of the structure adjacent theheater mat to greater than 0° C. when the structure is in a non-icingcondition; and determining a concentration of ice formed on thestructure based on a difference in the compared power and the powerdefined in the model.
 27. An aircraft comprising: a de-icing systemcomprising one or more heater mats thermally coupled to a structure ofthe aircraft; and a controller according to claim
 23. 28. An apparatusfor detecting ice formed on a structure, the apparatus comprising: aheater mat thermally coupleable to a structure for heating a firstregion of a structure adjacent to the heater mat; a temperature sensorfor outputting a temperature sensor signal indicative of a temperatureof the first region; a controller for controllably applying power toheater mat, the controller being adapted to: supply power to the heatermat, the power being sufficient to heat a surface of the structureadjacent the heater mat to greater than 0° C.; measure a surfacetemperature of the structure adjacent the heater mat over a firstperiod; compare the measured surface temperature over the first periodwith a model defining surface temperature characteristics of thestructure and heater mat; and detect ice formed on the structure basedon a difference between the measured surface temperature and the model.29. An apparatus according to claim 28, wherein the model definingsurface temperature characteristics of the structure and heater matcomprises data defining a temperature characteristic for a powersupplied to the heater mat when the structure has no ice on the surfaceor when the structure is in a non-icing condition.
 30. An apparatusaccording to claim 28, wherein the controller is adapted to determine aconcentration of ice formed on the structure by: comparing the powersupplied to the heater mat with a model defining powers sufficient todrive the heater mat such that the surface of the structure adjacent theheater mat to greater than 0° C. when the structure is in a non-icingcondition; and determining a concentration of ice formed on thestructure based on a difference in the compared power and the powerdefined in the model.
 31. An aircraft comprising the apparatus accordingto claim 28, wherein the heater mats are thermally coupled to theaircraft structure.
 32. A controller for detecting ice formed on astructure, the controller for controlling an ice protection system, thecontroller comprising: an output adapted to supply a first power to aheater mat of an ice protection system, the heater mat being thermallycoupleable to a structure for heating a first region of a structureadjacent to the heater mat; and an input adapted to receive atemperature sensor signal from a temperature sensor, the temperaturesensor signal indicating a temperature at a first region of a surfaceadjacent to a heater mat, the controller being adapted to: supply powerto the heater mat, the power being sufficient to heat the surface of thestructure adjacent the heater mat to greater than 0° C.; measure asurface temperature of the structure adjacent the heater mat over afirst period; compare the measured surface temperature over the firstperiod with a model defining surface temperature characteristics of thestructure and heater mat; and detect ice formed on the structure basedon a difference between the measured surface temperature and the model.33. A controller according to claim 32, wherein the model definingsurface temperature characteristics of the structure and heater matcomprises data defining a temperature characteristic for a powersupplied to the heater mat when the structure has no ice on the surfaceor when the structure is in a non-icing condition.
 34. A controlleraccording to claim 32, wherein the controller is adapted to determine aconcentration of ice formed on the structure by: comparing the powersupplied to the heater mat with a model defining powers sufficient todrive the heater mat such that the surface of the structure adjacent theheater mat to greater than 0° C. when a structure is in a non-icingcondition; and determining a concentration of ice formed on thestructure based on a difference in the compared power and the powerdefined in the model.
 35. An aircraft comprising: a de-icing systemcomprising one or more heater mats thermally coupled to a structure ofthe aircraft; and a controller according to claim 32.